Abstract
The global flow-field around an airfoil will be studied using time-resolved PIV technique. Interactions between pressure and suction sides flows will be studied in detail. Spanwise structures dynamics is to be analysed.
Highlights
The flow around an airfoil belongs to so-called canonical cases
The hypothesis of physical mechanism of flight relies on existence of streamwise vortical structures on the suction side of the airfoil and within its wake
The vortices origin is supposed to be the instability of the boundary layer subjected to adverse pressure gradient on the airfoil suction side – see [3]
Summary
The flow around an airfoil belongs to so-called canonical cases. It has been studied for very long period using all available methods – experimental and mathematical – see e.g. On the unexplored 3D instantaneous structure of the airfoil boundary layer on its suction side the new theory of flight by Hoffman and Johnson from KTH Stockholm is based, see [1, 2]. The hypothesis of physical mechanism of flight relies on existence of streamwise vortical structures on the suction side of the airfoil and within its wake. The vortices origin is supposed to be the instability of the boundary layer subjected to adverse pressure gradient on the airfoil suction side (i.e. upper) – see [3]
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